Modeling the effect of shock unsteadiness in shock-wave/turbulent boundary layer interactions

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Abstract

Reynolds averaged Navier-Stokes methods often cannot predict shock/turbulence interaction correctly. This may be because RANS models do not account for the unsteady motion of the shock wave that is inherent in these interactions. Sinha et al. [Phys. Fluids, Vol. 15, No. 8 (2003)] propose a shock-unsteadiness correction that significantly improves turbulence prediction across a normal shock in a uniform mean flow. In this paper, we generalize the modification to simulate complex flows using k-ε, k-ω, and Spalart-Allmaras models. In compression-corner flows, the corrected k-ε and k-ω models amplify the turbulent kinetic energy less through the shock compared to the standard models. This results in Improved prediction of the separation shock location, a delayed reattachment, and a slower recovery of the boundary layer on the ramp. In the Spalart-Allmaras model, the modification amplifies eddy viscosity across the shock, moving the separation location closer to the experiment.

Original languageEnglish (US)
Pages7183-7193
Number of pages11
DOIs
StatePublished - 2004
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 5 2004Jan 8 2004

Conference

Conference42nd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/5/041/8/04

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    Sinha, K., Mahesh, K., & Candler, G. V. (2004). Modeling the effect of shock unsteadiness in shock-wave/turbulent boundary layer interactions. 7183-7193. Paper presented at 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States. https://doi.org/10.2514/6.2004-1129